Masters Theses

Date of Award

12-1989

Degree Type

Thesis

Degree Name

Master of Science

Major

Aviation Systems

Major Professor

R. D. Kimberlin

Committee Members

R. L. Young, Uwe Peter Solies

Abstract

The Augusta A-109A II helicopter is currently marketed world-wide by the Italian firm Gruppo-Augusta as an executive or commercial transport, cargo carrier, or vehicle for emergency medical service (EMS). The purpose of this test was to conduct a flying qualities and performance evaluation of the aircraft with limited scope for the armed scout mission. The tests were conducted during one five hour ground evaluation, and three flights totalling six flight hours. The testing revealed a number of deficiencies which were categorized by the evaluator as Part I, II, and III deficiencies as defined in Appendix A. The most severe Part I deficiencies, which must be corrected prior to fleet delivery, are: first, the aircraft cannot hover in ground effect at maximum gross weight on an ICAO standard day above a pressure altitude of 7500 feet. The low IGE hover ceiling will require a download of fuel or ordnance to operate in nap of the earth (NOE) flight regimes at higher pressure altitudes. Second, the aircraft cannot hover out of ground effect (OGE) at maximum gross weight on an ICAO standard day above a pressure altitude of 3000 feet. The low OGE hover ceiling will require downloading of fuel or ordnance to operate in contour flight regimes at higher pressure altitudes. An additional 26 Part I deficiencies were identified. Twenty-three Part II deficiencies were identified which should be corrected as soon as practicable. Four Part III deficiencies were identified which should be avoided in future designs.

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